旋流器仿生叶片对流场特征的调控机制数值计算

班润泽; 董林; 李鹿辉; 彭海涛; 戴今; 孙磊; 魏静文

doi:10.13224/j.cnki.jasp.20250335

旋流器仿生叶片对流场特征的调控机制数值计算

doi: 10.13224/j.cnki.jasp.20250335

班润泽^1,,
董林^1,*, ,,
李鹿辉²,
彭海涛¹,
戴今¹,
孙磊¹,
魏静文¹

1.
上海工程技术大学机械与汽车工程学院，上海 201620
2.
北京航空航天大学国际创新学院，杭州 311115

基金项目: 国家自然科学基金重点项目（12232002）；国家自然科学基金青年科学基金（12002199）；国家自然科学基金面上项目（12072017）

详细信息

作者简介:
班润泽（1998-），男，硕士生，研究领域为航空发动机燃烧室孔系与旋流器。E-mail：www.woshiban@qq.com

通讯作者:
董林（1985-），女，副教授，博士，研究领域为航空发动机燃烧室旋流控制等。E-mail：donglin16@163.com

中图分类号: V231.2
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出版历程
- 收稿日期: 2025-07-16
- 网络出版日期: 2025-12-08

Numerical simulation of flow-field regulation mechanisms in swirlers via bionic blades

1.
School of Mechanical and Automobile Engineering，Shanghai University of Engineering Science，Shanghai 201620，China
2.
Hangzhou International Innovation Institute，Beihang University，Hangzhou 311115，China

摘要

摘要:
新型旋流器研发是提升燃烧室贫油熄火边界、优化典型工作工况中火焰稳定性的关键突破口。基于数值计算方法系统研究了一种融合翼果仿生特征的双级反向旋流器在燃烧室冷态流场中的特性演化规律，通过解析主燃级与值班级叶片设计类型对中心回流区的调控机制，揭示了不同叶片组合及后缘厚度变化对冷态流场的拓扑特征影响规律。结果显示：主燃级与值班级的叶片组合方案显著影响中心回流区涡核范围与速度分布，当叶片后缘削薄率为40%～60%临界值时，涡核区域面积及回流速度的增长率随削薄率增加呈非线性衰减趋势，但仍维持正相关性。其中，当主燃级叶片采用仿生设计时，有助于扩大涡核区域并提高回流速度，对中心回流区的影响范围集中于0.3≤x/D≤1.2与−0.3≤z/D≤0.3的空间区域；值班级叶片为仿生设计时，对涡心区域的扩展产生增强效应。
- 双级旋流器 /
- 仿生叶片 /
- 燃烧室流场 /
- 涡核 /
- 回流区
Abstract:
The development of novel swirlers represents a critical breakthrough for enhancing the lean blow-off limit of combustion chambers and optimizing flame stability under typical operating conditions. Based on a numerical approach, the characteristic evolution of a dual-stage counter-rotating swirler was systematically investigated by incorporating biomimetic features inspired by winged seeds within the cold-flow field of a combustor. By analyzing the control mechanisms of the main and pilot stage blade design types on the central recirculation zone (CRZ), the influences of different blade combinations and trailing-edge thickness variations on the topological characteristics of the cold flow field were revealed. Results indicated that the blade combination scheme of the main and pilot stages significantly affected the vortex core extent and velocity distribution within the CRZ. When the trailing-edge thinning ratio reached a critical value between 40% and 60%, the growth rates of both the vortex core area and the recirculation velocity exhibited a nonlinear decay trend with the increasing thinning ratio, yet maintained a positive correlation. Specifically, employing the biomimetic design for the main stage blades contributed to an expanded vortex core region and an increased recirculation velocity, with its dominant influence on the CRZ concentrated within the spatial domain of 0.3≤x/D≤1.2 and −0.3≤z/D≤0.3. Utilizing the biomimetic design for the pilot stage blades produced an enhancing effect on the expansion of the vortex core region.
- dual-stage swirler /
- bionic blades /
- flow characteristics /
- vortex core /
- recirculation zone

HTML

图 1 双级旋流器模型与剖视图

Figure 1. Sectional view and two-stage counter-rotating swirler model

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图 2 旋流叶片引入翼果外形特征设计示意图

Figure 2. Schematic diagram of swirler blade improvement

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图 3 带仿生叶片的双级反向旋流器3D打印实物模型

Figure 3. 3D-printed physical prototype of a dual-stage counter-swirling bionic-blade assembly

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图 4 流体域网格划分示意图

Figure 4. Computational grid generation for fluid region

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图 5 不同网格数目对应的轴向速度

Figure 5. Axial velocities corresponding to different numbers of grids

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图 6 y=0 mm截面轴向速度v_x/u云图

Figure 6. Contours of axial velocity v_x/u at y=0 mm section

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图 7 数值计算与 PIV 数据的中心线轴向速度对比分析

Figure 7. Comparative analysis of numerical calculations and PIV data for centerline axial velocity

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图 8 涡核区域示意图

Figure 8. Schematic diagram of the vortex core region

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图 9 不同叶片组合方案在x-z截面轴向速度云图

Figure 9. Axial velocity contours of different blade combination schemes in the x-z section

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图 10 不同方案中心轴线处的平均速度分布

Figure 10. Average velocity distribution at the central axes of different schemes

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图 11 不同方案中燃烧室头部轴向速度云图

Figure 11. Axial velocity contours of the combustion chamber head in different schemes

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图 12 不同方案对应的X-Z截面轴向平均速度分布云图

Figure 12. Contour plots of axial velocity distribution on the X-Z sections for different schemes

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图 13 各仿生方案中心线处的轴向速度分布及其局部放大图

Figure 13. Axial velocity distribution at the centerline of each bionic scheme and its local magnified images

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图 14 y-z平面下x/D=0.82处轴向时均速度v_x/u分布云图

Figure 14. Contours of the axial velocity v_x/u distribution at x/D=0.82 in the y-z section

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图 15 不同仿生方案的涡心周向中心线上轴向速度分布

Figure 15. Axial velocity distribution on the circumferential center line of the vortex core in different bionic schemes

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图 16 各方案回流速度3D等值面结构分布图

Figure 16. Three-dimensional iso-surface characterization of reflux velocity structures for different schemes

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表 1 翼果静态特征测量参数

Table 1. Static characteristic measurement parameters of samaras

参数	数值
叶弦长度/mm	20
后缘厚度/mm	0.2
前缘厚度/mm	0.5
叶凹凸幅度/mm	0.15
叶凹凸高度/mm	0.18
翼果质量/mg	49
叶脉数量	48
叶片宽度/mm	7.5
叶片长度/mm	16
果实长度/mm	8
果实厚度/mm	3.5
前后缘厚度差/mm	0.3

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表 2 叶片组合方案

Table 2. Blade combination scheme

组合方案	叶片类型		旋流数
组合方案	值班级叶片	主燃级叶片	值班级叶片	主燃级叶片
标准方案	S	S	0.6830	1.3379
Bio-A	B	S	0.6830	1.2356
Bio-B	S	B	0.6359	1.3379
Bio-C	B	B	0.6359	1.2356

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表 3 仿生叶片后缘厚度分配方案

Table 3. Thickness distribution scheme of the trailing edge of bionic blades

分配方案	叶片类型		最大削薄量/mm
分配方案	值班级	主燃级	前缘厚度	后缘厚度
方案A	B	B	1.5	0.6
方案B	B	B	1.5	0.9
方案C	B	B	1.5	1.2
方案D	S	S	1.5	1.5

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表 4 不同方案主燃级和值班级对应旋流数

Table 4. Corresponding swirl numbers for the main stage and the Pilot stage in different schemes

分配方案	旋流数S_n
分配方案	值班级叶片	主燃级叶片
方案A	0.6268	1.2222
方案B	0.6451	1.2592
方案C	0.6638	1.2977
方案D	0.6830	1.3379

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